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Modeling of Chill Down in Cryogenic Transfer Lines
Author(s) -
Matthew Cross,
Alok Majumdar,
John Bennett,
Ramesh B. Malla
Publication year - 2002
Publication title -
journal of spacecraft and rockets
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.758
H-Index - 79
eISSN - 1533-6794
pISSN - 0022-4650
DOI - 10.2514/2.3810
Subject(s) - spacecraft , aerospace engineering , missile , space (punctuation) , spacecraft design , systems engineering , space shuttle , space technology , space exploration , engineering , mechanical engineering , computer science , operating system
A numerical model to predict chill down in cryogenic transfer lines has been developed. Three chill down cases using hydrogen as the working fluid are solved: 1) a simplified model amenable to analytical solution, 2) a realistic model of superheated vapor flow, and 3) a realistic model of initially subcooled liquid flow. The first case compares a numerical model with an analytical solution with very good agreement between the two. Additionally, the analytical solution provides a convenient way to look at parametric effects on the chill down. The second and third cases are numerical models that provide temperature histories of the fluid and solid tube wall during chill down, as well as several other quantities of interest such as pressure and mass flow rate. Of great interest in chill down applications is the ability to predict accurate values of chill down time (the time required to achieve steady-state cryogenic flow). The models predict that a 66.04-cm-long, 0.48-cm-internal-diameter aluminum tube has a shorter chill down time (100 s) and uses less hydrogen with superheated vapor flow than with initially subcooled liquid flow (>200 s for chill down).

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